U.S. patent number 6,893,210 [Application Number 10/684,402] was granted by the patent office on 2005-05-17 for internal core profile for the airfoil of a turbine bucket.
This patent grant is currently assigned to General Electric Company. Invention is credited to Rachel Kyano Black, Anthony Aaron Chiurato, Xiuzhang James Zhang.
United States Patent |
6,893,210 |
Zhang , et al. |
May 17, 2005 |
Internal core profile for the airfoil of a turbine bucket
Abstract
First stage turbine buckets have internal core profiles
substantially in accordance with Cartesian coordinate values of X,
Y and Z set forth Table I wherein X and Y values are in inches and
the Z values are non-dimensional values convertible to Z distances
in inches by multiplying the Z values by the height of the airfoil
in inches. The X and Y values are distances which, when connected
by smooth continuing arcs, define internal core profile sections at
each distance Z. The profile sections at each distance Z are joined
smoothly to one another to form a complete internal core profile.
The X, Y and Z distances may be scalable as a function of the same
constant or number to provide a scaled up or scaled down internal
core profile. The nominal internal core profile given by the X, Y
and Z distances lies within an envelope of .+-.0.050 inches in
directions normal to any internal core surface location.
Inventors: |
Zhang; Xiuzhang James
(Simpsonville, SC), Chiurato; Anthony Aaron (Simpsonville,
SC), Black; Rachel Kyano (Greenville, SC) |
Assignee: |
General Electric Company
(Schenectady, NY)
|
Family
ID: |
34377604 |
Appl.
No.: |
10/684,402 |
Filed: |
October 15, 2003 |
Current U.S.
Class: |
415/116;
416/223A; 416/95; 416/96R; 416/DIG.2 |
Current CPC
Class: |
F01D
5/141 (20130101); F01D 5/18 (20130101); F01D
5/187 (20130101); Y10S 416/02 (20130101) |
Current International
Class: |
F01D
5/18 (20060101); F01D 5/14 (20060101); F04D
031/00 () |
Field of
Search: |
;415/115,116
;416/95,96R,97R,223A,DIG.2,DIG.5 |
References Cited
[Referenced By]
U.S. Patent Documents
|
|
|
5980209 |
November 1999 |
Barry et al. |
6722851 |
April 2004 |
Brittingham et al. |
|
Primary Examiner: Look; Edward K.
Assistant Examiner: White; Dwayne J.
Attorney, Agent or Firm: Nixon and Vanderhye
Claims
What is claimed is:
1. A turbine bucket including an airfoil, platform, shank and
dovetail, said airfoil having an internal nominal core profile
substantially in accordance with Cartesian coordinate values of X,
Y and Z set forth in Table I wherein the Z values are
non-dimensional values convertible to Z distances in inches by
multiplying the Z values by a height of the airfoil in inches, and
wherein X and Y are distances in inches which, when connected by
smooth continuing arcs, define internal core profile sections at
each distance Z along the airfoil, the profile sections at the Z
distances being joined smoothly with one another to form said
airfoil internal core profile.
2. A turbine bucket according to claim 1 wherein said airfoil has
side walls and ribs extending therebetween, said ribs being spaced
from one another between leading and trailing edges of the airfoil
and defining with internal wall surfaces of said side walls
internal cooling passages along the length of the airfoil, said
smooth continuing arcs extending along the internal wall surfaces
of the cooling passages and between adjacent passages along said
side walls.
3. A turbine bucket according to claim 2 wherein said smooth
continuing arcs pass through junctures between the ribs and each of
the side walls.
4. A turbine bucket according to claim 1 wherein said bucket
airfoil has an external airfoil shape, said internal core profile
sections including generally airfoil-shaped portions within the
bucket airfoil and generally conform to profile sections of said
external airfoil shape of the bucket airfoil less a wall thickness
therebetween.
5. A turbine bucket according to claim 1 forming part of a first
stage of a turbine.
6. A turbine bucket according to claim 1 wherein said internal core
profile lies in an envelope within .+-.0.050 inches in a direction
normal to any internal core surface location.
7. A turbine bucket including an airfoil, platform, shank and
dovetail, said airfoil having an internal nominal core profile
substantially in accordance with Cartesian coordinate values of X,
Y and Z set forth in Table I wherein the Z values are
non-dimensional values convertible to Z distances in inches by
multiplying the Z values by a height of the airfoil in inches, and
wherein X and Y are distances in inches which, when connected by
smooth continuing arcs, define internal core profile sections at
each Z distance along the airfoil, the profile sections at the Z
distances being joined smoothly with one another to form said
bucket airfoil internal core profile, the X, Y and Z distances
being scalable as a function of the same constant or number to
provide a scaled-up or scaled-down internal core profile.
8. A turbine bucket according to claim 7 wherein said airfoil has
side walls and ribs extending therebetween, said ribs being spaced
from one another between leading and trailing edges of the airfoil
and defining with internal wall surfaces of said side walls
internal cooling passages along the length of the airfoil, said
smooth continuing arcs extending along the internal wall surfaces
of the cooling passages and between adjacent passages along said
side walls.
9. A turbine bucket according to claim 7 wherein said smooth
continuing arcs pass through junctures between the ribs and each of
the side walls.
10. A turbine bucket according to claim 7 wherein said bucket
airfoil has an external airfoil shape, said internal core profile
sections including generally airfoil-shaped portions within the
bucket airfoil and generally conform to profile sections of said
external airfoil shape of the bucket airfoil less a wall thickness
therebetween.
11. A turbine bucket according to claim 7 wherein said integral
core shape lies in an envelope within .+-.0.050 inches in a
direction normal to any internal core surface location.
12. A turbine comprising a turbine wheel having a plurality of
buckets, each of said buckets including an airfoil, a platform, a
shank and a dovetail, each airfoil having an internal nominal core
profile substantially in accordance with Cartesian coordinate
values of X, Y and Z set forth in Table I wherein the Z values are
non-dimensional values convertible to Z distances in inches by
multiplying the Z values by a height of the airfoil in inches, and
wherein X and Y are distances in inches which, when connected by
smooth continuing arcs, define internal core profile sections at
each distance Z along the airfoil, the profile sections at the Z
distances being joined smoothly with one another to form said
bucket internal core profile.
13. A turbine according to claim 12 wherein each said airfoil has
side walls and ribs extending therebetween, said ribs being spaced
from one another between leading and trailing edges of the airfoil
and defining with internal wall surfaces of said side walls
internal cooling passages along the length of the airfoil, said
smooth continuing arcs extending along the internal wall surfaces
of the cooling passages and between adjacent passages along said
side walls.
14. A turbine according to claim 12 wherein said smooth continuing
arcs pass through junctures between the ribs and each of the side
walls.
15. A turbine according to claim 12 wherein each said bucket
airfoil has an external airfoil shape, said internal core profile
sections including generally airfoil-shaped portions within the
bucket airfoil and generally conforming to profile sections of said
external airfoil shape of the bucket airfoil less a wall thickness
therebetween.
16. A turbine according to claim 12 wherein the turbine wheel
comprises a first stage of the turbine.
17. A turbine according to claim 12 wherein the turbine wheel has
92 buckets and X represents a distance parallel to the turbine axis
of rotation.
18. A turbine according to claim 12 wherein the X, Y and Z
distances are scalable as a function of the same constant or number
to provide scaled-up or scaled-down internal core profile.
Description
BACKGROUND OF THE INVENTION
The present invention relates to a bucket of a stage of a gas
turbine and particularly relates to a first stage turbine bucket
airfoil internal core profile.
Many system requirements must be met for each stage of the hot gas
path section of a gas turbine in order to meet design goals
including overall improved efficiency and airfoil loading.
Particularly, the buckets of the first stage of the turbine section
must meet the operating requirements for that particular stage and
also meet requirements for bucket cooling flow, weight and bucket
life. Internal cooling requirements must be optimized,
necessitating a unique internal core airfoil profile to meet stage
performance requirements enabling the turbine to operate in a safe,
efficient and smooth manner.
BRIEF DESCRIPTION OF THE INVENTION
In accordance with the preferred embodiment of the present
invention there is provided a unique internal core profile for a
bucket airfoil of a gas turbine, preferably the first stage
airfoil, that enhances the performance of the gas turbine. It will
be appreciated that the external airfoil shape of the bucket
airfoil improves the interaction between various stages of the
turbine, and affords improved aerodynamic efficiency and improved
first stage airfoil aerodynamic and mechanical loading. The
external airfoil profile for the preferred bucket is set forth in a
companion application Ser. No. 10/446,688, filed May 29, 2003,
titled "Airfoil Shape for a Turbine Bucket," the disclosure of
which is incorporated by reference. Concomitantly, the internal
core shape of the airfoil is also significant for structural
reasons as well as to optimize internal cooling with appropriate
wall thickness. The airfoil internal core profile is defined by a
unique loci or points which achieves the necessary structural and
cooling requirements whereby improved turbine performance is
obtained. This unique loci of points define the internal nominal
core profile and are identified by the X, Y and Z Cartesian
coordinates of Table I which follows. The 1100 points for the
coordinate values shown in Table I are for a cold, i.e., room
temperature bucket airfoil at various cross-sections of the airfoil
along its length. The positive X, Y and Z directions are axial
toward the exhaust end of the turbine, tangential in the direction
of engine rotation looking aft and radially outwardly toward the
bucket tip, respectively. The X and Y coordinates are given in
distance dimensions, e.g., units of inches, and are joined smoothly
at each Z location to form a smooth continuous internal core
profile section. The Z coordinates are given in non-dimensionalized
form from Z=0.043 to Z=0.997. By multiplying the airfoil height
dimensions, e.g., in inches, by the non-dimensional Z value of
Table I, the internal core profile, of the airfoil is obtained.
Each defined internal core profile section in the X, Y plane is
joined smoothly with adjacent profile sections in the Z direction
to form the complete internal airfoil core profile.
The preferred first stage turbine bucket airfoil includes external
convex and concave, side wall surfaces with ribs extending
internally between and formed integrally with the side walls
defining the external side wall surfaces. The ribs are spaced from
one another between leading and trailing edges of the airfoil and
define with internal wall surfaces of the airfoil side walls
internal cooling passages, preferably serpentine in configuration,
along the length of the airfoil. The smooth continuing arcs
extending between the X, Y coordinates to define each profile
section at each distance Z extend along the internal wall surfaces
of the cooling passages and between adjacent passages along each of
the side walls to substantially conform to the adjacent external
wall surfaces. Consequently, each internal core profile section has
envelope portions which pass through the juncture or interface
between the ribs and each of the side walls as well as along the
side walls of the cooling passages between the ribs. These internal
core profile sections are generally airfoil in shape and generally
conform to the external airfoil shape of the bucket airfoil less
the wall thickness at each Z distance.
It will be appreciated that as each airfoil heats up in use, the
internal core profile will change as a result of mechanical loading
and temperature. Thus, the cold or room temperature profile is
given by the X, Y and Z coordinates for manufacturing purposes.
Because a manufactured internal bucket core profile may be
different from the nominal profile given by the following table, a
distance of plus or minus 0.050 inches from the nominal profile in
a direction normal to any surface location along the nominal
profile defines a profile envelope for this internal airfoil core
profile. The profile is robust to this variation without impairment
of the mechanical, cooling and aerodynamic functions of the
bucket.
It will also be appreciated that the airfoil can be scaled up or
scaled down geometrically for introduction into similar turbine
designs. Consequently, the X and Y coordinates in inches and the
non-dimensional Z coordinates, when converted to inches, of the
internal nominal core profile given below may be a function of the
same constant or number. That is, the X, Y and Z coordinate values
in inches may be multiplied or divided by the same constant or
number to provide a scaled up or scaled down version of the
internal airfoil core profile while retaining the core profile
section shape.
In a preferred embodiment according to the present invention, there
is provided a turbine bucket including an airfoil, platform, shank
and dovetail, the airfoil having an internal nominal core profile
substantially in accordance with Cartesian coordinate values of X,
Y and Z set forth in Table I wherein the Z values are
non-dimensional values convertible to Z distances in inches by
multiplying the Z values by a height of the airfoil in inches, and
wherein X and Y are distances in inches which, when connected by
smooth continuing arcs, define internal core profile sections at
each distance Z along the airfoil, the profile sections at the Z
distances being joined smoothly with one another to form the
airfoil internal core profile.
In a further preferred embodiment according to the present
invention, there is provided a turbine bucket including an airfoil,
platform, shank and dovetail, the airfoil having an internal
nominal core profile substantially in accordance with Cartesian
coordinate values of X, Y and Z set forth in Table I wherein the Z
values are non-dimensional values convertible to Z distances in
inches by multiplying the Z values by a height of the airfoil in
inches, and wherein X and Y are distances in inches which, when
connected by smooth continuing arcs, define internal core profile
sections at each Z distance along the airfoil, the profile sections
at the Z distances being joined smoothly with one another to form
the bucket airfoil internal core profile, the X, Y and Z distances
being scalable as a function of the same constant or number to
provide a scaled-up or scaled-down internal core profile.
In a further preferred embodiment according to the present
invention, there is provided a turbine comprising a turbine wheel
having a plurality of buckets, each of the buckets including an
airfoil, a platform, a shank and a dovetail, each airfoil having an
internal nominal core profile substantially in accordance with
Cartesian coordinate values of X, Y and Z set forth in Table I
wherein the Z values are non-dimensional values convertible to Z
distances in inches by multiplying the Z values by a height of the
airfoil in inches, and wherein X and Y are distances in inches
which, when connected by smooth continuing arcs, define internal
core profile sections at each distance Z along the airfoil, the
profile sections at the Z distances being joined smoothly with one
another to form the bucket internal core profile.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is a schematic representation of a hot gas path through
multiple stages of a gas turbine and illustrates a first stage
bucket airfoil according to a preferred embodiment of the present
invention;
FIG. 2 is a perspective view of a bucket according to a preferred
embodiment of the present invention with the bucket illustrated in
conjunction with its airfoil, platform and its substantially or
near axial entry dovetail connection;
FIG. 3 is a side elevational view of the bucket of FIG. 2 and
associated airfoil, platform and dovetail connection as viewed from
a generally circumferential direction;
FIG. 4 is a top view of the bucket;
FIG. 5 is an end view of the bucket as viewed looking in an
upstream direction; and
FIG. 6 is an enlarged generalized cross-sectional view taken along
a cut through the bucket airfoil to illustrate an internal core
profile hereof.
DETAILED DESCRIPTION OF THE INVENTION
Referring now to the drawings, particularly to FIG. 1, there is
illustrated a hot gas path, generally designated 10, of a gas
turbine 12 including a plurality of turbine stages. Three stages
are illustrated. For example, the first stage comprises a plurality
of circumferentially spaced nozzles 14 and buckets 16. The nozzles
are circumferentially spaced one from the other and fixed about the
axis of the rotor. The first stage buckets 16, of course, are
mounted on the turbine rotor 17. A second stage of the turbine 12
is also illustrated, including a plurality of circumferentially
spaced nozzles 18 and a plurality of circumferentially spaced
buckets 20 mounted on the rotor 17. The third stage is also
illustrated including a plurality of circumferentially spaced
nozzles 22 and buckets 24 mounted on rotor 17. It will be
appreciated that the nozzles and buckets lie in the hot gas path 10
of the turbine, the direction of flow of the hot gas through the
hot gas path 10 being indicated by the arrow 26.
Referring to FIG. 2, it will be appreciated that the buckets, for
example, the buckets 16 of the first stage are mounted on a rotor
wheel, not shown, forming part of rotor 17 and include platforms
30, shanks 32 and dovetails 34. Each bucket 16 is provided with a
substantially or near axial entry dovetail 34, e.g., about 15
degrees off-axis, for connection with a complementary-shaped mating
dovetail, not shown, on the rotor wheel. An axial entry dovetail,
however, may be provided. It will also be appreciated that each
bucket 16 has an external bucket airfoil 38 as illustrated in FIGS.
2 and 6. Thus, each of the buckets 16 has a bucket airfoil profile
at any cross-section from the airfoil platform 30 to the bucket tip
33 in the shape of an airfoil 38. In this preferred embodiment of a
first stage turbine bucket, there are ninety-two (92) bucket
airfoils. While not forming part of the present invention, each
first stage bucket 16 includes a plurality of internal, generally
serpentine-shaped, cooling passages 35 (FIG. 6) forming several air
cooling circuits extending from the platform to the tip of the
bucket airfoil. These air cooling circuits exhaust cooling air from
the airfoil 38 into the hot gas path at exit locations adjacent the
leading and trailing edges of the airfoil.
More particularly, each bucket airfoil 38 includes convex and
concave external wall surfaces, i.e., pressure and suction surfaces
42 and 44, respectively, (FIG. 6) which, with an internal core
profile 40, define an airfoil wall thickness "t." Each bucket 16
also includes a plurality of ribs 46 extending between or
projecting from opposite side walls 48 of the bucket. Ribs 46 are
spaced from one another between leading and trailing edges 52 and
54 of the bucket airfoil, respectively, and extend generally from
the platform 30 to the bucket airfoil tip 33 to define, with
internal wall surface portions 49 of bucket side walls 48, the
plurality of internal generally serpentine-shaped cooling passages
35. Certain of the ribs 46 terminate short of the tip of the
airfoil.
To define the internal core shape of each first stage bucket from
the platform 30 to the tip 33 of the bucket airfoil 38, there is
provided a unique set or loci of points in space that meet the
stage requirements, bucket cooling area and wall thickness and can
be manufactured. This unique loci of points, which defines the
internal bucket core profile 40, comprises a set of 1100 points
relative to the axis of rotation of the turbine. A Cartesian
coordinate system of X, Y and Z values given in Table 1 below
defines this internal core profile 40 of the airfoil 38 at various
locations along its length. The coordinate values for the X and Y
coordinates are set forth in inches in Table I although other units
of dimensions may be used when the values are appropriately
converted. The Z values are set forth in Table I in non-dimensional
form from Z=0.043 to Z=0.997. To convert the Z value to a Z
coordinate value, e.g., in inches, the non-dimensional Z value
given in the table is multiplied by the height of airfoil 38 in
inches. For this preferred first-stage bucket, the airfoil height
from the platform 30 to the tip of the airfoil is 6.3 inches. The
Z=0 non-dimensional coordinate for the preferred airfoil is 28.0
inches from the rotor centerline (engine axis). The Z=1
non-dimensional coordinate for the preferred airfoil is Z=32.3
inches from the rotor centerline (engine axis). The Cartesian
coordinate system has orthogonally-related X, Y and Z axes and the
X axis lies parallel to the turbine rotor centerline, i.e., the
rotary axis and a positive X coordinate value is axial toward the
aft, i.e., exhaust end of the turbine. The positive Y coordinate
value extends tangentially in the direction of rotation of the
rotor, looking aft, and the positive Z coordinate value is radially
outwardly toward the bucket tip.
By defining X and Y coordinate values at selected locations in a Z
direction normal to the X, Y plane, the internal core profile 40 of
the bucket, e.g., representatively illustrated by the dashed and
full lines in FIG. 6, at each Z distance along the length of the
airfoil can be ascertained. By connecting the X and Y values with
smooth continuing arcs, each internal core profile section thus
formed at each distance Z is fixed. The internal core profiles of
the various internal locations between the distances Z are
determined by smoothly connecting the adjacent profile sections to
one another to form the core profile. These values represent the
internal core profiles at ambient, non-operating or non-hot
conditions.
The smooth continuing arcs extending between the X, Y coordinates
to define each profile section at each distance Z extend along the
internal wall surface portions 49 and between adjacent passages 35
along each of the side walls 48 from the platform to the bucket
airfoil tip. Thus, each internal core profile 40 has envelope
portions which pass through the juncture between the ribs 46 and
the side walls 48 (represented by the dashed lines in FIG. 6) as
well as along the internal side walls of the cooling passages
(represented by the full lines in FIG. 6).
The Table I values are generated and shown to three decimal places
for determining the internal core profile of the bucket. There are
typical manufacturing tolerances as well as coatings which must be
accounted for in the actual internal profile of the airfoil.
Accordingly, the values for the profile given in Table I are for a
nominal internal airfoil core profile. It will therefore be
appreciated that .+-. typical manufacturing tolerances, i.e., .+-.
values, including any coating thicknesses, are additive to the X
and Y values given in Table I below. Accordingly, a distance of
.+-.0.050 inches in a direction normal to any surface location
along the internal core profile defines an internal core profile
envelope for this particular bucket design and turbine, i.e., a
range of variation between measured points on the actual internal
core profile at nominal cold or room temperature and the ideal
position of those points as given in the Table below at the same
temperature. The internal core profile is robust to this range of
variation without impairment of mechanical and cooling
functions.
The coordinate values given in Table I below provide the preferred
nominal internal core profile envelope.
TABLE I X Y Z X Y Z X Y Z -1.335 -0.336 0.043 -0.157 0.180 0.043
-1.374 -0.107 0.139 -1.278 -0.312 0.043 -0.095 0.173 0.043 0.157
0.530 0.139 -1.224 -0.281 0.043 -0.033 0.163 0.043 -1.014 -0.053
0.139 -1.170 -0.247 0.043 0.029 0.148 0.043 -1.059 -0.095 0.139
-1.118 -0.212 0.043 0.088 0.128 0.043 0.108 0.567 0.139 -1.067
-0.175 0.043 0.147 0.105 0.043 0.202 0.488 0.139 -1.019 -0.134
0.043 0.204 0.079 0.043 -1.378 -0.226 0.139 -0.970 -0.096 0.043
0.260 0.049 0.043 -0.964 -0.018 0.139 -0.919 -0.059 0.043 0.313
0.017 0.043 -0.912 0.016 0.139 -0.867 -0.023 0.043 0.366 -0.019
0.043 -1.108 -0.132 0.139 -0.814 0.012 0.043 0.416 -0.057 0.043
-1.323 -0.247 0.139 -0.759 0.042 0.043 0.464 -0.097 0.043 -1.389
-0.166 0.139 -0.703 0.070 0.043 0.511 -0.139 0.043 -1.195 0.142
0.139 -0.646 0.098 0.043 0.556 -0.183 0.043 -1.158 0.191 0.139
-0.589 0.124 0.043 0.599 -0.229 0.043 -0.881 0.050 0.139 -0.530
0.147 0.043 0.639 -0.277 0.043 -1.160 -0.166 0.139 -0.470 0.165
0.043 0.679 -0.326 0.043 0.055 0.598 0.139 -0.408 0.177 0.043 0.717
-0.376 0.043 0.245 0.443 0.139 -0.346 0.184 0.043 0.754 -0.427
0.043 -1.265 -0.229 0.139 -0.283 0.187 0.043 0.791 -0.479 0.043
-1.120 0.239 0.139 -0.154 0.669 0.043 0.825 -0.532 0.043 -1.081
0.287 0.139 -0.216 0.681 0.043 0.855 -0.587 0.043 -1.040 0.333
0.139 -0.279 0.686 0.043 0.910 -0.602 0.043 -0.999 0.379 0.139
-0.342 0.682 0.043 0.949 -0.559 0.043 -0.958 0.425 0.139 -0.404
0.672 0.043 0.924 -0.502 0.043 -0.915 0.469 0.139 -0.465 0.659
0.043 0.894 -0.446 0.043 -0.866 0.506 0.139 -0.526 0.642 0.043
0.865 -0.390 0.043 -0.813 0.537 0.139 -0.586 0.622 0.043 0.835
-0.335 0.043 -0.760 0.568 0.139 -0.644 0.599 0.043 0.803 -0.281
0.043 -0.706 0.598 0.139 -0.702 0.573 0.043 0.770 -0.227 0.043
-0.652 0.627 0.139 -0.757 0.543 0.043 0.736 -0.174 0.043 -0.595
0.652 0.139 -0.811 0.510 0.043 0.703 -0.121 0.043 -0.537 0.671
0.139 -0.863 0.475 0.043 0.670 -0.067 0.043 -0.477 0.687 0.139
-0.913 0.437 0.043 0.636 -0.014 0.043 -0.417 0.698 0.139 -0.961
0.397 0.043 0.598 0.036 0.043 -0.358 0.706 0.139 -1.007 0.353 0.043
0.557 0.084 0.043 -0.294 0.707 0.139 -1.049 0.306 0.043 0.516 0.132
0.043 -0.233 0.703 0.139 -1.088 0.257 0.043 0.476 0.180 0.043
-0.173 0.691 0.139 -1.126 0.207 0.043 0.435 0.229 0.043 -0.282
0.230 0.139 -1.163 0.156 0.043 0.395 0.277 0.043 -0.344 0.230 0.139
-1.198 0.104 0.043 0.355 0.325 0.043 -0.405 0.223 0.139 -1.233
0.051 0.043 0.314 0.373 0.043 -0.466 0.214 0.139 -1.266 -0.002
0.043 0.272 0.421 0.043 -0.527 0.205 0.139 -1.300 -0.055 0.043
0.230 0.467 0.043 -0.562 0.179 0.139 -1.335 -0.106 0.043 0.184
0.511 0.043 -0.639 0.156 0.139 -1.374 -0.157 0.043 0.135 0.550
0.043 -0.696 0.133 0.139 -1.402 -0.212 0.043 0.081 0.582 0.043
-0.754 0.110 0.139 -1.412 -0.274 0.043 0.025 0.609 0.043 -0.809
0.083 0.139 -1.383 -0.327 0.043 -0.034 0.633 0.043 -1.212 -0.198
0.139 -0.220 0.186 0.043 -0.094 0.653 0.043 -1.265 -0.229 0.139 X Y
Z X Y Z X Y Z 0.286 0.397 0.139 -1.328 -0.162 0.234 -0.190 0.258
0.234 0.521 0.113 0.139 -1.269 -0.158 0.234 -0.131 0.246 0.234
0.560 0.065 0.139 -1.216 -0.131 0.234 -0.073 0.232 0.234 0.598
0.016 0.139 -1.166 -0.098 0.234 -0.016 0.215 0.234 0.633 -0.034
0.139 -1.117 -0.064 0.234 0.040 0.194 0.234 0.666 -0.086 0.139
-1.069 -0.029 0.234 0.094 0.168 0.234 0.700 -0.138 0.139 -1.023
0.011 0.234 0.146 0.138 0.234 0.733 -0.190 0.139 -0.977 0.049 0.234
0.196 0.105 0.234 0.765 -0.242 0.139 -0.928 0.082 0.234 0.246 0.072
0.234 0.795 -0.296 0.139 -0.876 0.112 0.234 0.295 0.038 0.234 0.825
-0.349 0.139 -0.823 0.141 0.234 0.344 0.004 0.234 0.854 -0.404
0.139 -0.770 0.168 0.234 0.393 -0.032 0.234 0.883 -0.458 0.139
-0.716 0.193 0.234 0.440 -0.069 0.234 0.910 -0.513 0.139 -0.660
0.216 0.234 0.485 -0.108 0.234 0.881 -0.560 0.139 -0.604 0.236
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0.871 0.902 0.609 -0.161 0.902 -1.171 0.662 0.997 -1.017 0.837
0.902 0.584 -0.115 0.902 -1.140 0.629 0.997 -1.053 0.798 0.902
0.558 -0.069 0.902 -1.096 0.616 0.997 -1.086 0.758 0.902 0.533
-0.023 0.902 -1.050 0.615 0.997 -1.118 0.715 0.902 0.506 0.023
0.902 -1.004 0.620 0.997 -1.147 0.672 0.902 0.479 0.068 0.902
-0.959 0.630 0.997 -1.170 0.625 0.902 0.451 0.112 0.902 -0.914
0.642 0.997 -1.175 0.573 0.902 0.423 0.156 0.902 -0.870 0.654 0.997
-1.140 0.537 0.902 0.394 0.200 0.902 -0.825 0.664 0.997 -0.625
0.641 0.902 0.365 0.244 0.902 -0.780 0.673 0.997 -0.573 0.640 0.902
0.338 0.288 0.902 -0.734 0.678 0.997 -0.520 0.636 0.902 0.307 0.332
0.902 -0.688 0.681 0.997 -0.468 0.629 0.902 0.278 0.376 0.902
-0.131 0.863 0.997 -0.417 0.617 0.902 0.249 0.419 0.902 -0.167
0.891 0.997 -0.367 0.600 0.902 0.219 0.462 0.902 -0.204 0.918 0.997
X Y Z X Y Z X Y Z -0.318 0.581 0.902 0.187 0.505 0.902 -0.242 0.944
0.997 -0.270 0.560 0.902 0.154 0.545 0.902 -0.282 0.968 0.997
-0.223 0.537 0.902 0.120 0.585 0.902 -0.322 0.990 0.997 -0.177
0.512 0.902 0.084 0.624 0.902 -0.364 1.011 0.997 -0.142 0.843 0.902
0.049 0.662 0.902 -0.406 1.028 0.997 -0.186 0.872 0.902 0.012 0.700
0.902 -0.450 1.043 0.997 -0.231 0.900 0.902 -0.025 0.738 0.902
-0.494 1.056 0.997 -0.277 0.925 0.902 -0.062 0.774 0.902 -0.539
1.064 0.997 -0.324 0.948 0.902 -0.101 0.810 0.902 -0.642 0.681
0.997 -0.373 0.967 0.902 0.598 -0.263 0.902 -0.596 0.678 0.997
-0.423 0.981 0.902 0.624 -0.308 0.902 -0.550 0.672 0.997 -0.475
0.991 0.902 0.650 -0.354 0.902 -0.505 0.663 0.997 -0.527 0.996
0.902 0.675 -0.400 0.902 -0.460 0.652 0.997 -0.580 0.997 0.902
0.710 -0.433 0.902 -0.416 0.639 0.997 -0.132 0.485 0.902 0.730
-0.394 0.902 -0.373 0.624 0.997 -0.088 0.456 0.902 0.706 -0.347
0.902 -0.330 0.606 0.997 -0.045 0.425 0.902 0.682 -0.300 0.902
-0.288 0.587 0.997 -0.003 0.393 0.902 0.659 -0.253 0.902 -0.248
0.565 0.997 X Y Z -0.208 0.542 0.997 0.213 0.186 0.997 0.243 0.152
0.997 0.274 0.117 0.997 0.304 0.082 0.997 0.333 0.046 0.997 0.362
0.010 0.997 0.390 -0.026 0.997 0.418 -0.062 0.997 0.446 -0.099
0.997 0.477 -0.133 0.997 0.522 -0.135 0.997 0.553 -0.103 0.997
0.550 -0.059 0.997 0.527 -0.018 0.997 0.504 0.021 0.997 0.482 0.062
0.997 0.459 0.102 0.997 0.436 0.142 0.997 0.412 0.181 0.997 0.388
0.220 0.997 0.364 0.260 0.997 0.339 0.298 0.997 0.314 0.337 0.997
0.289 0.376 0.997 0.263 0.414 0.997 0.236 0.452 0.997 0.210 0.489
0.997 0.182 0.526 0.997 0.154 0.563 0.997 0.126 0.599 0.997 0.096
0.634 0.997 0.066 0.669 0.997 0.036 0.704 0.997 0.004 0.737 0.997
-0.028 0.770 0.997 -0.062 0.802 0.997 -0.096 0.833 0.997 -0.168
0.518 0.997 -0.130 0.493 0.997
-0.093 0.466 0.997 -0.056 0.438 0.997 -0.020 0.409 0.997 X Y Z
0.015 0.379 0.997 0.050 0.349 0.997 0.084 0.318 0.997 0.117 0.286
0.997 0.149 0.253 0.997 0.181 0.220 0.997 0.213 0.186 0.997
It will also be appreciated that the internal core profile of the
airfoil disclosed in the above Table may be scaled up or down
geometrically for use in other similar turbine designs.
Consequently, the coordinate values set forth in Table 1 may be
scaled upwardly or downwardly such that the internal profile shape
of the airfoil remains unchanged. A scaled version of the
coordinates in Table 1 would be represented by X, Y and Z
coordinate values of Table 1, with the non-dimensional Z coordinate
value converted to inches, multiplied or divided by a constant
number.
While the invention has been described in connection with what is
presently considered to be the most practical and preferred
embodiment, it is to be understood that the invention is not to be
limited to the disclosed embodiment, but on the contrary, is
intended to cover various modifications and equivalent arrangements
included within the spirit and scope of the appended claims.
* * * * *